GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 529 AIRFOIL (goe529-il) Reynolds number: 500,000 Max Cl/Cd: 108.95 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe529-il-500000-n5.txt Download as CSV file: xf-goe529-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 529 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2705 0.11782 0.11552 -0.0358 1.0000 0.0087
-10.750 -0.2673 0.11471 0.11244 -0.0364 1.0000 0.0086
-10.500 -0.2654 0.11136 0.10911 -0.0370 1.0000 0.0087
-10.250 -0.2591 0.10702 0.10479 -0.0393 0.9919 0.0089
-10.000 -0.2528 0.10142 0.09919 -0.0432 0.9826 0.0093
-9.750 -0.2416 0.09638 0.09414 -0.0478 0.9715 0.0095
-9.500 -0.2216 0.09204 0.08978 -0.0536 0.9606 0.0097
-9.250 -0.1918 0.08842 0.08612 -0.0605 0.9484 0.0101
-9.000 -0.1597 0.08402 0.08166 -0.0689 0.9307 0.0108
-8.750 -0.1373 0.07783 0.07536 -0.0778 0.9024 0.0118
-8.500 -0.1379 0.07188 0.06926 -0.0824 0.8646 0.0123
-8.250 -0.1380 0.06900 0.06627 -0.0833 0.8363 0.0127
-8.000 -0.1378 0.06690 0.06409 -0.0835 0.8145 0.0129
-7.750 -0.1321 0.06469 0.06181 -0.0848 0.7954 0.0132
-7.500 -0.1251 0.06203 0.05908 -0.0869 0.7774 0.0136
-7.250 -0.1171 0.05897 0.05593 -0.0895 0.7590 0.0143
-7.000 -0.1269 0.04584 0.04261 -0.1014 0.7437 0.0165
-6.500 -0.1197 0.01921 0.01422 -0.1136 0.7190 0.0212
-6.250 -0.0969 0.01815 0.01293 -0.1132 0.7036 0.0221
-6.000 -0.0719 0.01790 0.01256 -0.1128 0.6880 0.0226
-5.750 -0.0466 0.01766 0.01218 -0.1125 0.6743 0.0234
-5.500 -0.0215 0.01718 0.01151 -0.1121 0.6637 0.0243
-5.250 0.0039 0.01643 0.01054 -0.1118 0.6557 0.0253
-4.750 0.0555 0.01512 0.00881 -0.1112 0.6437 0.0270
-4.500 0.0819 0.01465 0.00817 -0.1110 0.6382 0.0275
-4.250 0.1082 0.01420 0.00754 -0.1107 0.6332 0.0278
-4.000 0.1336 0.01300 0.00610 -0.1104 0.6287 0.0289
-3.750 0.1602 0.01251 0.00552 -0.1101 0.6242 0.0299
-3.500 0.1868 0.01214 0.00505 -0.1099 0.6199 0.0305
-3.250 0.2137 0.01180 0.00461 -0.1096 0.6157 0.0310
-3.000 0.2408 0.01149 0.00423 -0.1094 0.6115 0.0316
-2.750 0.2678 0.01121 0.00388 -0.1092 0.6075 0.0321
-2.500 0.2947 0.01098 0.00357 -0.1089 0.6037 0.0326
-2.250 0.3218 0.01074 0.00329 -0.1087 0.5997 0.0332
-2.000 0.3490 0.01055 0.00306 -0.1085 0.5953 0.0342
-1.750 0.3761 0.01039 0.00285 -0.1083 0.5912 0.0350
-1.250 0.4306 0.01012 0.00250 -0.1078 0.5832 0.0363
-1.000 0.4578 0.00999 0.00234 -0.1076 0.5784 0.0371
-0.750 0.4848 0.00988 0.00219 -0.1074 0.5739 0.0392
-0.500 0.5121 0.00980 0.00210 -0.1072 0.5696 0.0418
-0.250 0.5394 0.00972 0.00204 -0.1070 0.5643 0.0451
0.000 0.5663 0.00966 0.00200 -0.1068 0.5589 0.0546
0.250 0.5934 0.00960 0.00198 -0.1066 0.5536 0.0730
0.500 0.6205 0.00955 0.00197 -0.1064 0.5468 0.0894
0.750 0.6471 0.00952 0.00197 -0.1062 0.5386 0.1082
1.000 0.6736 0.00951 0.00197 -0.1059 0.5277 0.1277
1.250 0.6997 0.00950 0.00199 -0.1055 0.5131 0.1543
1.500 0.7255 0.00952 0.00201 -0.1052 0.4979 0.1846
1.750 0.7513 0.00950 0.00207 -0.1048 0.4848 0.2315
2.000 0.7722 0.00879 0.00223 -0.1039 0.4727 0.6132
2.500 0.8406 0.00838 0.00243 -0.1067 0.4479 1.0000
2.750 0.8656 0.00855 0.00253 -0.1061 0.4382 1.0000
3.000 0.8910 0.00871 0.00263 -0.1057 0.4290 1.0000
3.250 0.9162 0.00888 0.00274 -0.1052 0.4213 1.0000
3.500 0.9417 0.00904 0.00286 -0.1047 0.4138 1.0000
3.750 0.9668 0.00921 0.00300 -0.1042 0.4070 1.0000
4.000 0.9923 0.00937 0.00313 -0.1038 0.4002 1.0000
4.500 1.0427 0.00971 0.00344 -0.1029 0.3872 1.0000
4.750 1.0676 0.00990 0.00361 -0.1024 0.3805 1.0000
5.000 1.0927 0.01007 0.00378 -0.1020 0.3743 1.0000
5.250 1.1174 0.01026 0.00396 -0.1015 0.3668 1.0000
5.500 1.1418 0.01048 0.00417 -0.1010 0.3572 1.0000
5.750 1.1652 0.01074 0.00438 -0.1003 0.3436 1.0000
6.000 1.1887 0.01100 0.00461 -0.0996 0.3322 1.0000
6.250 1.2115 0.01130 0.00486 -0.0988 0.3177 1.0000
6.500 1.2326 0.01170 0.00517 -0.0978 0.2953 1.0000
6.750 1.2518 0.01221 0.00555 -0.0965 0.2683 1.0000
7.000 1.2706 0.01274 0.00595 -0.0951 0.2457 1.0000
7.250 1.2890 0.01328 0.00639 -0.0937 0.2227 1.0000
7.500 1.3064 0.01387 0.00688 -0.0922 0.2006 1.0000
7.750 1.3156 0.01493 0.00763 -0.0894 0.1466 1.0000
8.000 1.3254 0.01588 0.00840 -0.0867 0.1177 1.0000
8.250 1.3380 0.01652 0.00900 -0.0843 0.1054 1.0000
8.750 1.3513 0.01831 0.01055 -0.0779 0.0560 1.0000
9.000 1.3552 0.01940 0.01157 -0.0746 0.0355 1.0000
9.250 1.3573 0.02066 0.01274 -0.0712 0.0173 1.0000
9.500 1.3663 0.02159 0.01370 -0.0689 0.0145 1.0000
9.750 1.3768 0.02247 0.01465 -0.0670 0.0129 1.0000
10.000 1.3871 0.02340 0.01566 -0.0651 0.0120 1.0000
10.250 1.3964 0.02445 0.01679 -0.0633 0.0114 1.0000
10.500 1.4035 0.02571 0.01814 -0.0614 0.0106 1.0000
10.750 1.4093 0.02714 0.01966 -0.0597 0.0100 1.0000
11.000 1.4141 0.02874 0.02134 -0.0580 0.0094 1.0000
11.250 1.4207 0.03026 0.02295 -0.0566 0.0091 1.0000
11.500 1.4272 0.03186 0.02463 -0.0554 0.0087 1.0000
11.750 1.4323 0.03365 0.02651 -0.0543 0.0082 1.0000
12.000 1.4361 0.03565 0.02859 -0.0533 0.0078 1.0000
12.250 1.4389 0.03781 0.03084 -0.0524 0.0075 1.0000
12.500 1.4405 0.04019 0.03332 -0.0516 0.0074 1.0000
12.750 1.4402 0.04284 0.03607 -0.0510 0.0072 1.0000
13.000 1.4355 0.04607 0.03939 -0.0505 0.0069 1.0000
13.250 1.4318 0.04928 0.04271 -0.0501 0.0067 1.0000
13.500 1.4311 0.05223 0.04576 -0.0498 0.0066 1.0000
13.750 1.4296 0.05535 0.04899 -0.0498 0.0065 1.0000
14.000 1.4271 0.05870 0.05244 -0.0498 0.0063 1.0000
14.250 1.4236 0.06223 0.05608 -0.0500 0.0062 1.0000
14.500 1.4217 0.06568 0.05963 -0.0503 0.0060 1.0000
14.750 1.4172 0.06958 0.06363 -0.0508 0.0059 1.0000
15.000 1.4137 0.07343 0.06759 -0.0514 0.0058 1.0000
15.250 1.4099 0.07741 0.07167 -0.0521 0.0056 1.0000
15.500 1.4068 0.08139 0.07574 -0.0530 0.0055 1.0000
15.750 1.4052 0.08523 0.07968 -0.0539 0.0053 1.0000
16.000 1.4013 0.08947 0.08401 -0.0550 0.0052 1.0000
16.250 1.3976 0.09374 0.08836 -0.0562 0.0051 1.0000
16.500 1.3929 0.09822 0.09294 -0.0575 0.0050 1.0000
16.750 1.3877 0.10283 0.09764 -0.0589 0.0049 1.0000
17.000 1.3816 0.10764 0.10253 -0.0605 0.0048 1.0000
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